SG122040A1 - Airfoil with three-pass serpentine cooling channeland microcircuit - Google Patents

Airfoil with three-pass serpentine cooling channeland microcircuit

Info

Publication number
SG122040A1
SG122040A1 SG200508439A SG200508439A SG122040A1 SG 122040 A1 SG122040 A1 SG 122040A1 SG 200508439 A SG200508439 A SG 200508439A SG 200508439 A SG200508439 A SG 200508439A SG 122040 A1 SG122040 A1 SG 122040A1
Authority
SG
Singapore
Prior art keywords
channeland
microcircuit
airfoil
serpentine cooling
pass serpentine
Prior art date
Application number
SG200508439A
Inventor
Frank J Cunha
Bret Teller
Young Chon
Dominic Mongillo
Edward F Pietraszkiewicz
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of SG122040A1 publication Critical patent/SG122040A1/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/13—Two-dimensional trapezoidal
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/10—Two-dimensional
    • F05D2250/18—Two-dimensional patterned
    • F05D2250/185—Two-dimensional patterned serpentine-like
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
SG200508439A 2004-11-02 2005-10-27 Airfoil with three-pass serpentine cooling channeland microcircuit SG122040A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/979,597 US7131818B2 (en) 2004-11-02 2004-11-02 Airfoil with three-pass serpentine cooling channel and microcircuit

Publications (1)

Publication Number Publication Date
SG122040A1 true SG122040A1 (en) 2006-05-26

Family

ID=36203890

Family Applications (1)

Application Number Title Priority Date Filing Date
SG200508439A SG122040A1 (en) 2004-11-02 2005-10-27 Airfoil with three-pass serpentine cooling channeland microcircuit

Country Status (7)

Country Link
US (1) US7131818B2 (en)
EP (1) EP1669546B1 (en)
JP (1) JP2006132536A (en)
KR (1) KR20060052313A (en)
CN (1) CN1800588A (en)
SG (1) SG122040A1 (en)
TW (1) TWI279481B (en)

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US7530789B1 (en) * 2006-11-16 2009-05-12 Florida Turbine Technologies, Inc. Turbine blade with a serpentine flow and impingement cooling circuit
US7731481B2 (en) * 2006-12-18 2010-06-08 United Technologies Corporation Airfoil cooling with staggered refractory metal core microcircuits
US7775768B2 (en) * 2007-03-06 2010-08-17 United Technologies Corporation Turbine component with axially spaced radially flowing microcircuit cooling channels
US10156143B2 (en) * 2007-12-06 2018-12-18 United Technologies Corporation Gas turbine engines and related systems involving air-cooled vanes
US8172533B2 (en) * 2008-05-14 2012-05-08 United Technologies Corporation Turbine blade internal cooling configuration
US8177507B2 (en) * 2008-05-14 2012-05-15 United Technologies Corporation Triangular serpentine cooling channels
US8157527B2 (en) * 2008-07-03 2012-04-17 United Technologies Corporation Airfoil with tapered radial cooling passage
US8348614B2 (en) * 2008-07-14 2013-01-08 United Technologies Corporation Coolable airfoil trailing edge passage
US8572844B2 (en) * 2008-08-29 2013-11-05 United Technologies Corporation Airfoil with leading edge cooling passage
US8303252B2 (en) 2008-10-16 2012-11-06 United Technologies Corporation Airfoil with cooling passage providing variable heat transfer rate
US8109725B2 (en) * 2008-12-15 2012-02-07 United Technologies Corporation Airfoil with wrapped leading edge cooling passage
US8353669B2 (en) * 2009-08-18 2013-01-15 United Technologies Corporation Turbine vane platform leading edge cooling holes
US8511994B2 (en) * 2009-11-23 2013-08-20 United Technologies Corporation Serpentine cored airfoil with body microcircuits
US9121290B2 (en) * 2010-05-06 2015-09-01 United Technologies Corporation Turbine airfoil with body microcircuits terminating in platform
US8535006B2 (en) 2010-07-14 2013-09-17 Siemens Energy, Inc. Near-wall serpentine cooled turbine airfoil
US10060264B2 (en) 2010-12-30 2018-08-28 Rolls-Royce North American Technologies Inc. Gas turbine engine and cooled flowpath component therefor
US9017027B2 (en) 2011-01-06 2015-04-28 Siemens Energy, Inc. Component having cooling channel with hourglass cross section
US8764394B2 (en) 2011-01-06 2014-07-01 Siemens Energy, Inc. Component cooling channel
US9022736B2 (en) 2011-02-15 2015-05-05 Siemens Energy, Inc. Integrated axial and tangential serpentine cooling circuit in a turbine airfoil
US9017025B2 (en) 2011-04-22 2015-04-28 Siemens Energy, Inc. Serpentine cooling circuit with T-shaped partitions in a turbine airfoil
US9127561B2 (en) * 2012-03-01 2015-09-08 General Electric Company Turbine bucket with contoured internal rib
US9296039B2 (en) 2012-04-24 2016-03-29 United Technologies Corporation Gas turbine engine airfoil impingement cooling
US9243502B2 (en) 2012-04-24 2016-01-26 United Technologies Corporation Airfoil cooling enhancement and method of making the same
US20130280081A1 (en) * 2012-04-24 2013-10-24 Mark F. Zelesky Gas turbine engine airfoil geometries and cores for manufacturing process
US10100646B2 (en) * 2012-08-03 2018-10-16 United Technologies Corporation Gas turbine engine component cooling circuit
KR101573409B1 (en) 2014-10-21 2015-12-01 연세대학교 산학협력단 Injections and arrangement of film cooling holes with backward injections
US10294799B2 (en) * 2014-11-12 2019-05-21 United Technologies Corporation Partial tip flag
WO2016160029A1 (en) * 2015-04-03 2016-10-06 Siemens Aktiengesellschaft Turbine blade trailing edge with low flow framing channel
US10502066B2 (en) 2015-05-08 2019-12-10 United Technologies Corporation Turbine engine component including an axially aligned skin core passage interrupted by a pedestal
US10323524B2 (en) 2015-05-08 2019-06-18 United Technologies Corporation Axial skin core cooling passage for a turbine engine component
FR3037107B1 (en) * 2015-06-03 2019-11-15 Safran Aircraft Engines ANNULAR ROOM OF COMBUSTION CHAMBER WITH OPTIMIZED COOLING
US10208605B2 (en) 2015-10-15 2019-02-19 General Electric Company Turbine blade
US10370978B2 (en) 2015-10-15 2019-08-06 General Electric Company Turbine blade
US10174620B2 (en) 2015-10-15 2019-01-08 General Electric Company Turbine blade
US10443398B2 (en) 2015-10-15 2019-10-15 General Electric Company Turbine blade
US10208671B2 (en) 2015-11-19 2019-02-19 United Technologies Corporation Turbine component including mixed cooling nub feature
US9932838B2 (en) * 2015-12-21 2018-04-03 General Electric Company Cooling circuit for a multi-wall blade
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US10633980B2 (en) 2017-10-03 2020-04-28 United Technologies Coproration Airfoil having internal hybrid cooling cavities
US10626733B2 (en) 2017-10-03 2020-04-21 United Technologies Corporation Airfoil having internal hybrid cooling cavities
US10626734B2 (en) 2017-10-03 2020-04-21 United Technologies Corporation Airfoil having internal hybrid cooling cavities
US10704398B2 (en) 2017-10-03 2020-07-07 Raytheon Technologies Corporation Airfoil having internal hybrid cooling cavities
EP3492702A1 (en) * 2017-11-29 2019-06-05 Siemens Aktiengesellschaft Internally-cooled turbomachine component
US10626735B2 (en) 2017-12-05 2020-04-21 United Technologies Corporation Double wall turbine gas turbine engine blade cooling configuration
US11028702B2 (en) * 2018-12-13 2021-06-08 Raytheon Technologies Corporation Airfoil with cooling passage network having flow guides
US11149550B2 (en) 2019-02-07 2021-10-19 Raytheon Technologies Corporation Blade neck transition
US10871074B2 (en) 2019-02-28 2020-12-22 Raytheon Technologies Corporation Blade/vane cooling passages
US11002638B2 (en) 2019-03-22 2021-05-11 Raytheon Technologies Corporation Multi-zone automatic magnetoscop inspection system
JP6636668B1 (en) * 2019-03-29 2020-01-29 三菱重工業株式会社 High-temperature component, method for manufacturing high-temperature component, and method for adjusting flow rate
JP6666500B1 (en) 2019-03-29 2020-03-13 三菱重工業株式会社 High temperature component and method of manufacturing high temperature component
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Also Published As

Publication number Publication date
TW200619494A (en) 2006-06-16
EP1669546B1 (en) 2011-06-29
JP2006132536A (en) 2006-05-25
US7131818B2 (en) 2006-11-07
KR20060052313A (en) 2006-05-19
CN1800588A (en) 2006-07-12
EP1669546A3 (en) 2009-12-02
EP1669546A2 (en) 2006-06-14
TWI279481B (en) 2007-04-21
US20060093480A1 (en) 2006-05-04

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